GB1267623A - Control apparatus for a gas turbine engine - Google Patents

Control apparatus for a gas turbine engine

Info

Publication number
GB1267623A
GB1267623A GB05750/70A GB1575070A GB1267623A GB 1267623 A GB1267623 A GB 1267623A GB 05750/70 A GB05750/70 A GB 05750/70A GB 1575070 A GB1575070 A GB 1575070A GB 1267623 A GB1267623 A GB 1267623A
Authority
GB
United Kingdom
Prior art keywords
speed
stop
engine
temperature
gas turbine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
GB05750/70A
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines GmbH
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of GB1267623A publication Critical patent/GB1267623A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/32—Control of fuel supply characterised by throttling of fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/263—Control of fuel supply by means of fuel metering valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/02—Purpose of the control system to control rotational speed (n)
    • F05D2270/021—Purpose of the control system to control rotational speed (n) to prevent overspeed
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/11—Purpose of the control system to prolong engine life
    • F05D2270/112—Purpose of the control system to prolong engine life by limiting temperatures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/303—Temperature

Abstract

1,267,623. Gas turbine engine fuel systems. MOTOREN-UND TURBINEN-UNION MUNCHEN G.m.b.H. April 2, 1970 [April 5, 1969], No. 15750/70. Heading F1G. A gas turbine engine fuel control comprises a speed governor controlling the fuel supply and having a control element movable for increasing and decreasing the set point of engine speed, stop means for preventing the movement, when this is in the sense to increase the speed, beyond a position corresponding to a predetermined maximum temperature at a particular location in the flow path of the engine working fluid, and means for sensing the engine temperature at that location and, when the sensed temperature rises above a certain value, acting to advance the stop means to stop the element short of the said position. The fuel supply from a fuel pump 12 to a gas turbine engine is controlled in accordance with engine speed by a control unit 6, the speed being selected by an arm 13 actuated by a selector lever 15. The maximum speed and therefore the maximum temperature in a free power turbine downstream of the engine or in a jet pipe, is set by a stop lever 6 which limits the movement of the arm 13, and is urged against a stop 20 by a spring 22. Compressor discharge pressure is applied via a line 24 directly to a chamber 26 at one side of a piston 17 and through a variable restrictor 25 to a chamber 27 on the other side. If the exhaust gas temperature exceeds a certain value, a temperature senser 18 opens a valve 28 to vent the chamber 27, whereupon the piston 17 moves the stop lever 16 towards a stop 19, thereby reducing the maximum speed which can be selected by the arm 13.
GB05750/70A 1969-04-05 1970-04-02 Control apparatus for a gas turbine engine Expired GB1267623A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE1917625A DE1917625C3 (en) 1969-04-05 1969-04-05 Fuel control device for the gas generator of a gas turbine plant

Publications (1)

Publication Number Publication Date
GB1267623A true GB1267623A (en) 1972-03-22

Family

ID=5730463

Family Applications (1)

Application Number Title Priority Date Filing Date
GB05750/70A Expired GB1267623A (en) 1969-04-05 1970-04-02 Control apparatus for a gas turbine engine

Country Status (4)

Country Link
US (1) US3653206A (en)
DE (1) DE1917625C3 (en)
FR (1) FR2030882A5 (en)
GB (1) GB1267623A (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3771314A (en) * 1971-10-04 1973-11-13 Gen Electric Gas turbine engine emergency speed control system
US3974645A (en) * 1974-08-08 1976-08-17 Westinghouse Electric Corporation Control apparatus for matching the exhaust flow of a gas turbine employed in a combined cycle electric power generating plant to the requirements of a steam generator also employed therein
US3973391A (en) * 1974-08-08 1976-08-10 Westinghouse Electric Corporation Control apparatus for modulating the inlet guide vanes of a gas turbine employed in a combined cycle electric power generating plant as a function of load or inlet blade path temperature
US5142860A (en) * 1990-06-18 1992-09-01 United Technologies Corporation Constant thrust retention turbine temperature limit system
US7107773B2 (en) * 2003-09-04 2006-09-19 Siemens Power Generation, Inc. Turbine engine sequenced combustion

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3133416A (en) * 1958-11-20 1964-05-19 Bendix Corp Braking system for gas turbine driven land vehicles
DE1136538B (en) * 1961-03-02 1962-09-13 Daimler Benz Ag Fuel control system for gas turbine engines
GB1032767A (en) * 1961-09-14 1966-06-15 Plessey Co Ltd Improvements in or relating to control systems for liquid-fuel supply for engines
GB1087795A (en) * 1964-09-24 1967-10-18 Bristol Siddeley Engines Ltd Improvements relating to control apparatus for rotary wing aircraft
US3531936A (en) * 1968-12-20 1970-10-06 Bendix Corp Integrating fluid meter with phase lead

Also Published As

Publication number Publication date
US3653206A (en) 1972-04-04
DE1917625C3 (en) 1975-03-06
DE1917625A1 (en) 1970-12-10
FR2030882A5 (en) 1970-11-13
DE1917625B2 (en) 1974-07-18

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